EP 3006680 B1 20180131 - AIRCRAFT GAS TURBINE ENGINE WITH IMPACT-ABSORBING ELEMENT FOR FAN BLADE LOSS
Title (en)
AIRCRAFT GAS TURBINE ENGINE WITH IMPACT-ABSORBING ELEMENT FOR FAN BLADE LOSS
Title (de)
FLUGGASTURBINENTRIEBWERK MIT STOSSDÄMPFUNGSELEMENT FÜR FANSCHAUFELVERLUST
Title (fr)
TURBINE A GAZ VOLATIL DOTE D'UN ELEMENT AMORTISSEUR POUR PERTE DE PALE DE VENTILATEUR
Publication
Application
Priority
DE 102014220317 A 20141007
Abstract (en)
[origin: US2016097301A1] An aircraft gas-turbine engine having a fan mounted on a fan shaft and including several fan blades, where the fan shaft is mounted on an engine structure by means of an upstream fan bearing, when seen in the flow direction, and a downstream bearing, where at least one predetermined breaking point is provided in the area of the fan bearing, characterized in that at least one shock-absorbing element designed as metal fabric damper is arranged at a radial gap to have a parallel effect relative to the predetermined breaking point.
IPC 8 full level
F01D 21/04 (2006.01); F01D 25/16 (2006.01)
CPC (source: EP US)
F01D 21/045 (2013.01 - EP US); F01D 25/06 (2013.01 - US); F01D 25/164 (2013.01 - EP US); F02C 7/06 (2013.01 - US); F16C 27/04 (2013.01 - EP US); F16C 2360/23 (2013.01 - EP US)
Designated contracting state (EPC)
AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR
DOCDB simple family (publication)
EP 3006680 A1 20160413; EP 3006680 B1 20180131; DE 102014220317 A1 20160407; US 2016097301 A1 20160407
DOCDB simple family (application)
EP 15188713 A 20151007; DE 102014220317 A 20141007; US 201514876435 A 20151006